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Virtual Design Method for Controlled Failure in Foldcore Sandwich Panels

Sturm, Ralf and Fischer, Sebastian (2015) Virtual Design Method for Controlled Failure in Foldcore Sandwich Panels. Applied Composite Materials. Springer. doi: 10.1007/s10443-015-9436-5. ISSN 0929-189X.

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For certification, novel fuselage concepts have to prove equivalent crashworthiness standards compared to the existing metal reference design. Due to the brittle failure behaviour of CFRP this requirement can only be fulfilled by a controlled progressive crash kinematics. Experiments showed that the failure of a twin-walled fuselage panel can be controlled by a local modification of the core through-thickness compression strength. For folded cores the required change in core properties can be integrated by a modification of the fold pattern. However, the complexity of folded cores requires a virtual design methodology for tailoring the fold pattern according to all static and crash relevant requirements. In this context a foldcore micromodel simulation method is presented to identify the structural response of a twin-walled fuselage panels with folded core under crash relevant loading condition. The simulations showed that a high degree of correlation is required before simulation can replace expensive testing. In the presented studies, the necessary correlation quality could only be obtained by including imperfections of the core material in the micromodel simulation approach.

Item URL in elib:https://elib.dlr.de/113097/
Document Type:Article
Title:Virtual Design Method for Controlled Failure in Foldcore Sandwich Panels
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Date:February 2015
Journal or Publication Title:Applied Composite Materials
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:Yes
Keywords:crash, explicit simulation, sandwich structures, foldcore, energy absorption
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Structures and Materials (old)
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Sturm, Ralf
Deposited On:18 Sep 2017 15:35
Last Modified:31 Jul 2019 20:10

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